CN110145969B - Missile interception method and server - Google Patents

Abstract

The invention provides a missile interception method and a server. The missile interception method includes: detecting the flight trajectory and flight speed of the incoming missile; calculating the preset launch time and the preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interceptor carries sub-munitions; The interceptor is launched at the preset launch time, and flies along the preset flight trajectory, thereby entering the ammunition dropping area for the incoming missile at the first moment; the interceptor is in the ammunition dropping area Submunitions are dropped on the incoming missile so that the submunitions detonate in the interception area to destroy the incoming missile. The missile interception and interception method and server of the present invention can remove various suspicious targets carried by the missile in a wide range by deploying sub-and-mother ammunition groups near the flight trajectory of the incoming missile, thereby protecting the safety of the party attacked by the missile.

Description

Missile interception method and server

This application is a divisional application for an invention patent with an application date of January 8, 2019, application number 201910014107.4, and the patent name is "missile interceptor".

technical field

The invention relates to the technical field of missile defense, in particular to a missile interception method and a server.

Background technique

With the rapid development of missile weapon technology, it has gradually become the core weapon in modern warfare. It can be said that missile weapons are the epitome of a country's military strength. In order to improve the effectiveness of missile attack, it usually has a certain penetration capability, which is also an important indicator of whether the missile can survive.

For the defending side, in order to avoid being attacked by missiles, it is necessary to effectively intercept the missiles of the attacking side. At present, the United States, Russia and other military powers are accelerating the establishment of missile defense systems.

In addition, missiles often carry multiple warheads or a large number of decoys and other penetration technologies when attacking targets. Traditional missile interception is often exhausted in actual combat. There is an urgent need for a missile interceptor that can intercept missiles equipped with multiple penetration technologies. To protect your own safety.

SUMMARY OF THE INVENTION

Aiming at the above technical problems in the prior art, the present invention provides a missile interception method and a server. Sub-munitions can be deployed in the flight trajectory of the incoming missile or in the nearby area, and can clear various suspicious targets carried by the missile in flight in a wide range.

One aspect of the present invention provides a missile interception method, comprising:

S1 detects the flight trajectory and flight speed of the incoming missile; S2 calculates the preset launch time and preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interceptor carries sub-munitions; S3 makes the The interceptor is launched at the preset launch time, and flies along the preset flight trajectory, thereby entering the ammunition release area for the incoming missile at the first moment; S4, the interceptor is directed to the ammunition release area in the ammunition release area. The incoming missiles drop submunitions such that the submunitions detonate in the interception area to destroy the incoming missile.

In one embodiment, the detecting the flight trajectory and flight speed of the incoming missile includes: detecting the radar reflection of the incoming missile and its surrounding area, so as to calculate the boundary range of the interception area according to the radar reflection; The interceptor drops sub-munitions into the interception area in the drop area, so that the sub-munition destroys the incoming missile in the interception area. The dropped sub-munitions are detonated by delay fuzes and/or trigger fuzes when they meet the boundary of the interception area to destroy suspicious targets within the boundary.

In one embodiment, the predetermined flight trajectory of the interceptor at least partially coincides with the mid-course flight trajectory of the incoming missile, and the interceptor drops submunitions before contacting the boundary area, so that the submunitions The charge moves relative to the incoming missile along the coincident portion, and the submunitions detonate upon at least partial intersection with the boundary range.

In one embodiment, the interceptor drops submunitions according to the shape and shape changes of the boundary range, so that the dropped submunitions move toward the incoming missile in a first three-dimensional shape, and are in contact with the boundary. Detonate when at least 50% of the ranges meet each other.

In one embodiment, the first three-dimensional shape is an umbrella with an opening toward the incoming missile, a cone with a tip toward the incoming missile, a rhombus with a rhomboid angle toward the incoming missile, and an axis with an axis aligned with the incoming missile. At least one of the cylindrical shapes having the same flight trajectory of the incoming missile.

In one embodiment, the size of the first three-dimensional shape is greater than the boundary range in at least two spatial dimensions.

In one embodiment, the interceptor enters within the boundary range at the second moment, and drops and detonates submunitions within the boundary range, thereby destroying targets within the boundary range.

In one embodiment, the sub-munitions are detonated when the degree of coincidence with the boundary range reaches a maximum to destroy suspicious targets within the boundary range.

In one embodiment, the interceptor drops sub-munitions at the munitions delivery area into the interception area, whereby the sub-munitions are detonated in the interception area to destroy the incoming missile comprising: monitoring the boundary range in space The movement speed and shape change of the munitions, and according to the movement speed and shape changes, calculate the release timing, release interval, release batch, and the number of child munitions dropped in each batch; the interceptor Dropping sub-munitions into the interception area in the ammunition release area, so that the sub-munitions are detonated in the interception area to destroy the incoming missile includes: the interceptor according to the release timing, release interval, release batch, each time The number of submunitions delivered in the batch delivers submunitions to the boundary range so that the dropped submunitions are detonated by time delay fuzes and/or trigger fuzes upon intersection with the boundary range.

In one embodiment, before dropping the sub-munitions, the interceptor further includes: calculating the relative speed and relative position of the interceptor and the boundary range, and selecting the timing of dropping the sub-munitions accordingly, and according to the boundary The shape and shape variation of the range selects the drop batches, the drop interval between batches, and the number of sub-munitions in each batch.

In one embodiment, the release batches of the sub-munitions include a first batch, an intermediate batch and a final batch in sequence according to the release time, and the number of sub-munitions in the intermediate batch is larger than that of the first batch The number of sub-munitions delivered to the last batch and said final batch.

In one embodiment, the intermediate batch includes multiple batches, and the number of sub-munitions put in each intermediate batch is greater than the number of sub-munitions put in the first batch and the final batch respectively .

In one embodiment, the release batches of the sub-munitions include multiple, and from the first batch to the last batch, the release interval of the sub-munitions first decreases and then increases, and the quantity of the sub-munitions to be dropped in each batch Increase first and then decrease.

Yet another aspect of the present invention provides a server, wherein the server includes a memory and a processor, where the memory stores an executable program, and the processor is configured to call the executable program, thereby executing the missile interception according to the embodiment of the present invention method.

The missile interceptor provided by the embodiments of the present invention can clear the incoming missile and various incoming targets carried by the incoming missile in a large space by deploying a large number of sub-munitions on the flight trajectory of the incoming missile.

After reading the detailed description and reviewing the accompanying drawings, those skilled in the art will recognize additional features and advantages.

Description of drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the accompanying drawings required in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some of the present invention. In the embodiments, for those of ordinary skill in the art, other drawings can also be obtained according to these drawings without any creative effort.

FIG. 1 is a block diagram of a missile interceptor according to an embodiment of the present invention.

FIG. 2 is a schematic flowchart of a missile interception method according to an embodiment of the present invention.

FIG. 3 is a schematic diagram of an interceptor dropping multiple batches of sub-munitions to attack an incoming target according to an embodiment of the present invention.

FIG. 4 is a schematic diagram of a boundary range of an interception area according to an embodiment of the present invention.

5 is a schematic diagram of the sub-munition and the incoming target flying relative to each other and the flight trajectory at least partially overlaps with the sub-munition according to the embodiment of the present invention.

6a-6e are schematic diagrams of shapes of sub-munitions deployed in space according to an embodiment of the present invention.

Detailed ways

The technical solutions of the present invention are further described below with reference to the accompanying drawings and through specific embodiments. Spatial relational terms such as "below," "below," "below," "lower," "above," "above," "higher," etc. are used to facilitate description to explain an element relative to a The orientation of the two elements means that these terms are intended to encompass different orientations of the device in addition to orientations other than those shown in the figures. In addition, for example, "one element is on/under the other" can mean that two elements are in direct contact with each other, or that there are other elements between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be regarded as limiting. Similar terms refer to similar elements throughout the description.

In describing the present invention, two similar terms, ie, incoming missile and incoming target, are simultaneously used. Those skilled in the art should understand that the entities referred to by different nouns are not substantially different. During the initial launch of a ballistic missile, all suspected targets to be deployed are carried by the ballistic missile. As the ballistic missile gets farther and farther from the earth, it gradually enters the mid-flight phase. For example, after a ballistic missile enters the mid-flight phase, its payload such as true warheads, dummy warheads, decoys, and other penetration measures are released, and these targets travel together in space. It can be seen that these targets are part of the original ballistic missile detachment, so they can be called incoming missiles. Also, since these targets are suspicious targets, they can also be called suspicious targets. The specific entities referred to by different words used in this application may be considered to be similar. For example, these referents can be only real warheads, or real warheads containing a large number of fake targets, or multiple warheads or a combination of multiple warheads and several fake targets, and so on. Those skilled in the art shall not narrow, change or distort the protection scope of the present invention by making limited interpretations of the above words.

Taking a ballistic missile as an example, its defense includes take-off phase defense, ascending phase defense, mid-course defense and terminal-phase defense. Ballistic missiles fly for a relatively long time in the mid-course, and the defender has more opportunities to take defensive measures. Therefore, the establishment of a mid-course defense system is also the focus of ballistic missile defense. However, in order to ensure the penetration capability of ballistic missiles, ballistic missiles (especially ballistic missiles carrying nuclear weapons) are usually equipped with various penetration methods. These penetration methods include fake warheads, decoys, aluminum foil, etc., to interfere with the radar detection of the defender, so that the defender cannot identify the real warhead target from many targets, so that the real warhead can break through the defender under the cover of these cover devices. missile defense system. In addition, when the payload is multiple warheads, it is almost impossible for the traditional collision interception method to intercept all missile warheads, so that a large number of real warheads will attack the defender's homeland, which will cause damage to the national security of the attacked party. serious threat.

The missile interceptor of the present invention can be used for intercepting incoming missiles carrying multiple warheads or equipped with a large number of penetration measures such as aluminum foils or decoys, can sweep away a large number of incoming warheads and decoys, and is especially suitable for intercepting incoming ballistics in the middle section missile. However, the scope of application of the present invention is not limited to intercepting ballistic missiles, and may also be other types of incoming missiles.

The present invention provides a missile interceptor. Referring to FIG. 1 , the missile interceptor 2 may include: a signal receiver 100 , a controller 200 , a propulsion mechanism 300 , and an ammunition dispersing mechanism 400 . The ammunition distributing mechanism 400 stores sub-unit ammunition. The signal receiver 100 is configured to receive an ignition command signal, and the controller 200 is configured to control the propulsion mechanism 300 to ignite when the signal receiver 100 receives the ignition command signal, so as to push the missile interceptor into a preset state. flight trajectory. The controller 200 is further configured to control the dispersing mechanism 400 to release the sub-munitions at the preset flight trajectory, so as to form a group of sub-munitions for intercepting incoming targets. The missile interceptor of the present invention can clear the incoming targets in a wide range by distributing the sub-municipal ammunition groups in the preset flight trajectory, which greatly reduces the requirement for identifying the true and false incoming targets.

For example, the submunitions are equipped with time delay fuzes and/or trigger fuzes, and the controller 200 is used to control the detonation of submunitions that intersect with the incoming target to destroy the incoming target. Among them, the controller 200 can control the detonation time of the sub-munitions, so as to maximize the destruction of the incoming target. For example, when both submunitions are equipped with trigger fuzes, the submunitions detonate upon contact with an incoming target.

For example, the propulsion mechanism 300 can be a conventional solid propulsion system, specifically a solid rocket propulsion system or a solid missile propulsion system.

In addition, the present invention also provides a missile interception method. 2, the missile interception method includes: S1 detects the flight trajectory and flight speed of the incoming missile; S2 calculates the preset launch time and preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interception The interceptor carries sub-munitions; S3 makes the interceptor launch at the preset launch time, and flies along the preset flight trajectory, so as to enter the ammunition release area for the incoming missile at the first moment; S4 The interceptor drops sub-munitions on the incoming missile at the munitions release area, so that the sub-munitions detonate in the interception area to destroy the incoming missile. The mid-section interception method of the ballistic missile of the present invention can destroy suspicious targets including the incoming missile in a large range by deploying the sub-munitions on the flight trajectory of the incoming missile, greatly reducing the requirements for the interception accuracy of the ballistic missile, and improving the success of missile interception Rate.

For example, in step S1, a ground-based mid-section radar may be used to detect the flight trajectory and flight speed of the incoming missile. For example, the flight trajectory of an incoming missile can be determined by tracking the radar over a period of time, and the flight speed can be calculated by detecting the position of the incoming missile at two points in time and the time it takes to pass through the two positions. In addition, reconnaissance satellites deployed in space can also be used to detect the flight trajectory and speed of ballistic missiles. In this case, for example, the reconnaissance satellite can return information about the flight speed and flight trajectory of the missile to the ground in real time, so that the ground defense system can launch the interceptor according to the flight speed and flight trajectory of the missile in real time.

The sub-munitions referred to in the present invention may include, for example, small bombs that can be deployed in a wide range of space, or small nuclear bombs that can be independently detonated. The choice of sub-munitions can be determined according to the characteristics of the incoming target. For example, when the sub-munitions are small bombs, the more the incoming missile comes from a military power, the larger the explosive power of the small bomb tends to be (mainly considering that most of the warheads of military powers have adopted certain strengthening measures). For example, in the case where the sub-munition is a small nuclear bomb, since the nuclear bomb can destroy the incoming target with a high probability, there is no specific requirement for the yield of the small nuclear bomb. However, since a nuclear bomb explodes in outer space, it will also pose a certain threat to the homeland. Therefore, the smaller the yield of a small nuclear bomb, the better, and the principle is to try not to detonate the opponent's nuclear bomb. In addition, it should be understood that the value of destroying the nuclear bomb carried by the opponent's missile through a small nuclear bomb is far greater than the harm caused by the explosion of the small nuclear bomb in outer space (even including the harm caused by the small nuclear bomb may detonate the opponent's nuclear bomb to the country). In order to avoid possible nuclear explosions in outer space as much as possible, the sub-munitions of the present invention are preferably conventional munitions. For example, these sub-munitions can be independently equipped with guidance systems (for example, the guidance systems can be infrared-guided or satellite-guided) for more precise interception of incoming targets in a wide range.

In the missile interceptor and the mid-section interception method of the present invention, a large number of sub-munitions released by the missile interceptor can be distributed in space, which is equivalent to setting a large number of explosion points at intervals within a certain range of space. These explosion points can not only directly destroy the incoming target through the explosion, but also multiple explosion points can form a high temperature center after the explosion, so that all suspicious targets entering the high temperature center are destroyed or burned. For example, each explosion point can be detonated by delayed detonation or by impact detonation. And preferably, each explosion point is equipped with two detonation methods at the same time, so as to avoid the missed target phenomenon that may be caused by a single impact detonation and the situation of low attack accuracy caused by a single delayed detonation.

Referring to Figure 3, for example, in order to improve the probability of destroying the threat target, the incoming target (within the range of the rectangular structure in Figure 3, including incoming missiles and other suspicious targets, but the rectangular structure is only for illustration, The shape of the boundary formed by the incoming target is not limited to the flying direction S1 of the rectangle) 1, and multiple sub-munition groups 21, 22, 23 are deployed at intervals to implement multi-stage destruction on the incoming target 1. For example, the first sub-munition group 21 closest to the incoming target 1 may contain the most sub-munitions. For example, the number of sub-munitions in each batch of sub-munition groups can be progressively decreased as the distance from the incoming missile increases. In this case, the submunitions contained in the first batch of submunitions group 21 can carry out the first wave of destruction on the suspected target. For example, suspicious target 1 was mostly destroyed after the first wave of destruction. Under special circumstances (for example, some warheads use super explosion-proof and high-temperature protection measures), the second batch of sub-munitions group 22 can be used to carry out secondary destruction to some fish that slip through the net. At this time, since the suspicious target 1 has been damaged to a certain extent after being destroyed by the first batch of sub-munition munitions, it can be easily destroyed after being hit by the second wave of sub-munition munitions. For example, only a small number of sub-munitions in the third batch of sub-munitions group 23 can be deployed to destroy the remaining targets that may exist. The missile interceptor and the interception method of the embodiments of the present invention further improve the success rate of missile interception by carrying out multi-level destruction on the incoming target, thereby better protecting the national homeland security.

In one embodiment, referring to FIG. 4 , other suspicious targets 12 may also be included in flight with the incoming missile 11 . The real warhead 11 and other suspicious targets 12 can cover a certain area in space, for example. For example, when the missile deploys a real warhead and various penetration measures, it is difficult to detect the location of the real warhead by conventional detection methods. Therefore, in order to catch all kinds of suspicious targets in the above coverage area, the sub-munitions can be deployed using the boundary 13 of the coverage area as a reference for the interception area. Specifically, the detection device may draw the boundary range of the interception area for suspicious targets according to the detected radar reflection signal area. The embodiments of the present invention can better deploy sub-munitions by drawing the boundary range of suspicious targets, thereby improving the interception probability of various suspicious targets.

In some embodiments, for example, the boundary range of the suspicious target can also be detected in real time by the detector of the missile interceptor, or the ground detection device cooperates with the detector on the missile interceptor, so that the controller can determine the boundary of the target according to the range, and control the ammunition distributing mechanism to release ammunition.

In one embodiment, the detecting the flight trajectory and the flight speed S1 of the incoming missile may include: detecting the radar reflection of the incoming missile and its surrounding area, so as to calculate the boundary range of the interception area according to the radar reflection 13. The controller 200 of the interceptor 2 can drop sub-munitions into the interception area 13 in the drop area, so that the sub-munitions destroy the incoming missile S4 in the interception area 13, including: the control of the interceptor 2 The controller 200 controls the ammunition dispersing mechanism 400 to release sub-munitions according to the boundary range 13 of the interception area, so that the controller 200 controls the dropped sub-munitions to pass the time delay fuze and/or The fuze is triggered to detonate to destroy suspicious targets within said boundary 13 . The missile interceptor of the embodiment of the present invention can completely remove suspicious targets within the boundary range by detonating the boundary range of suspicious targets and detonating by delaying and/or triggering a fuze, thereby greatly improving the success rate of interception.

It should be noted that the area where the missile interceptor 2 drops the sub-munitions may be outside the boundary range of the suspicious target, and the dropping area may also partially overlap with the boundary range or be within the boundary range. For example, in the case of a missile interceptor moving relative to a suspicious target, the drop zone can be in front of the suspicious target's movement (the front refers to the suspicious target in the direction of the suspicious target's movement), so that the dropped submunitions can have more Sufficient time to disperse and deploy to achieve overall destruction of suspicious targets in a better spatial arrangement.

Referring to FIG. 5 , in one embodiment, the preset flight trajectory of the controller 200 of the interceptor 2 is at least partially coincident with the flight trajectory of the incoming target 11 during the mid-flight period (the overlapping part is indicated by the reference numeral 3 in the figure). ballistic segment). The controller 200 of the interceptor 2 can control the ammunition distributing mechanism 400 to drop the sub-munitions 21 , 22 before contacting the boundary area 13 , so that the sub-munitions 21 , 22 are aligned along the overlapping portion 13 with the incoming munitions. The target 1 moves relatively, and the controller 200 controls the submunitions 21 , 22 to detonate upon at least partial intersection with the boundary range 13 .

In this embodiment, the interceptor 2 shown in FIG. 5 drops submunitions before reaching the coincident ballistic portion, so that these submunitions meet the incoming target 1 at the coincidence portion 3 after entering the coincidence portion 3 . For example, before the interceptor 2 reaches the coincident ballistic 3, the interceptor 2 may release the sub-munitions from top to bottom, so that the sub-munitions enter the coincident ballistic 3. After that, for example, the interceptor 2 can enter the coincident trajectory 3, so that the interceptor collides with the incoming target 1 in the coincident trajectory 3, thereby further improving the probability of successful interception. In this case, for example, the interceptor could have terminal infrared or radar guidance and drive the interceptor through thrusters to hit the most suspicious targets.

In this embodiment, the interceptor 2 can also fly in the reverse direction in the flight trajectory of the incoming target 1, so that the interceptor 2 can release the sub-munitions ahead of the moving direction of the interceptor 2 before meeting the incoming target 1. Under normal circumstances, the detonation speed of conventional explosives is 1000-8500 m/s, and the speed of ballistic missiles during mid-flight is also 3000-6000 m/s. It can be seen that when the sub-munitions are detonated when they meet the incoming target part, Its blast shock wave can quickly spread to all incoming targets, so as to achieve the purpose of destroying the target.

In addition, the controller 200 can also calculate the shape and diffusion of the explosion shock wave when the sub-munitions are detonated according to the distribution of the sub-munitions, the distance between the sub-munitions, and the explosive power of each sub-munition, so as to make the interception area The center encounters the shock wave at its maximum spread (on the basis of its ability to destroy the incoming real warhead), further increasing the destruction effectiveness of the incoming target.

In the embodiment of the present invention, by partially overlapping the flight trajectory of the interceptor with the flight trajectory of the incoming target, and by making the two fly relative to each other, the impact force of the interceptor, the sub-munitions and the incoming target can be improved, and the sub-munitions can be ensured. The destructive effect of the blast shock wave on the incoming target.

Referring to FIG. 6a, in one embodiment, the controller 200 of the interceptor 2 may control the ammunition distributing mechanism 400 to drop the sub-munitions 21 according to the shape and shape change of the boundary range, so that the dropped sub-munitions 21 are in the first three-dimensional The shape moves toward the incoming target 1, and the controller 200 can control the sub-munitions 21 to detonate after meeting at least 50% of the boundary range with each other. In Fig. 6a, h is the length of the incoming target 1 in its flight direction, and h1 is the intersection length of the submunitions 21 and the incoming target 1. The embodiments of the present invention detonate when at least 50% of the sub-munitions and the boundary area meet each other, and can better destroy various incoming targets within the border by allowing a large number of sub-munitions to enter the border area filled with suspicious targets. , thereby further increasing the probability of destroying a true warhead. In order to improve the effectiveness of the destruction of suspicious targets, the proportion of the above-mentioned rendezvous portion may be greater than 70%.

It should be pointed out that, according to the illustration in Figure 6a, the sub-munitions and the incoming target are very close to each other after they meet. But in fact, the incoming targets are often spread over a large range in space (that is, the sub-munitions are far away from the incoming targets), so it is difficult for the scattered sub-munitions to come with each other without using the navigation and guidance method. The attacking target is directly hit, which is one of the reasons why the traditional impact interception method is difficult to intercept the attacking target in the middle section.

Referring to Figures 6b-6e, in this embodiment, for example, the first three-dimensional shape is an umbrella with an opening toward the incoming missile, a cone with a cone tip toward the incoming missile, and a diamond angled toward the incoming missile. At least one of the rhombus of the missile and the cylinder whose axis is in the same direction as the flight trajectory of the incoming missile. The embodiment of the present invention can better destroy the incoming target by further arranging the spatial shape of the sub-munition ammunition. For example, when the sub-munition adopts an umbrella structure, the sub-munition can be detonated by a delay fuze when most of the suspicious targets fall into the umbrella opening. Similarly, when the sub-munitions are arranged in a cylindrical shape, the sub-munitions can be detonated after all the suspicious targets enter the barrel, so as to achieve surrounding blasting from the periphery of the suspicious target to the suspicious target, thereby further improving the probability of destroying the suspicious target.

It should be pointed out that, on the one hand, the first three-dimensional shape can be formed by dropping the sub-munitions in batches at intervals. However, only by using this mode of interval and batch delivery, the sub-munitions can only form a relatively simple arrangement. On the other hand, the first three-dimensional shape can also be achieved by the ammunition dispensing mechanism. That is, the sub-munition ammunition is shaped for release by the ammunition distributing mechanism 400, so that the sub-munition ammunition forms a specific shape when it is released. For example, the first three-dimensional shape can also be realized by sending flight control commands to the sub-munitions through the controller of the interceptor, so as to control the movement attitude and speed of the sub-munitions.

In the above embodiment, the size of the first three-dimensional shape is larger than the boundary range in at least two dimensions. For example, the dimensions of the first three-dimensional shape in each of the three dimensions may be 5% larger than the corresponding dimensions of the bounding range of suspicious targets, thereby better destroying these suspicious targets. For example, the size of the umbrella mouth of the sub-munition deployed in the umbrella shape is suspected to be larger than the size of the boundary range in this direction, and the diameter of the cylindrical opening is larger than the maximum size of the boundary range of the suspected target in the same direction. By adjusting the size of the first three-dimensional shape, all suspicious targets can be inserted into the openings of the deployed sub-munitions, thereby further improving the destruction effectiveness of the suspicious targets.

For example, the controller 200 may control the submunitions dispersed in the air to detonate when the degree of coincidence or intersection with the boundary range is maximized to destroy suspicious targets within the boundary range. For example, when the encirclement space formed by the dispersed submunitions is larger than the size of the border range of the suspected target, the submunitions can be detonated when all suspicious targets enter the encirclement space, thereby increasing the destruction effectiveness of the suspected target.

In one embodiment, the interceptor can also enter the boundary range 13 of the suspicious target 1 at the second moment, and drop and detonate sub-munitions 21 within the boundary range 13, thereby destroying the boundary range 13 target within 13. When the ammunition carried by the interceptor 2 is conventional ammunition, since the relative movement speed of the interceptor 2 and the incoming target 1 is extremely high, the scattered ammunition is often detonated before it can be dispersed. In this case, the range that the explosion can reach is greatly reduced, so that some suspicious targets located close to the border cannot be destroyed. Therefore, in this embodiment, the interceptor 2 can preferably carry a small nuclear bomb, so that the small nuclear bomb can destroy all suspicious targets from within the boundary range of the suspicious targets.

In one embodiment, the interceptor further includes a detector, and the detector is used to monitor the movement speed and shape change of the boundary range in space, and the controller 200 calculates the movement speed and shape change according to the movement speed and shape change. The release timing, release interval, batches of sub-munitions, and the number of sub-munitions in each batch. The controller controls the ammunition distributing mechanism to release the sub-munitions to the boundary range according to the delivery timing, the release interval, the release batch, and the quantity of the sub-munitions released in each batch, so that the dropped sub-munitions are in the same range as the said sub-munitions. Detonated by delayed fuze and/or trigger fuze at or before boundary range rendezvous. The embodiment of the present invention can further improve the accuracy of the target by determining the timing of the release, the release interval, the release batch, and the number of sub-munitions dropped in each batch according to the moving speed and shape change of the boundary range of the suspicious target in the air Destruction effectiveness of suspicious targets.

For example, the detector 200 can calculate the relative speed and relative position of the interceptor and the boundary range, the controller selects the release timing of the sub-munitions accordingly, and selects the release batch according to the shape and shape change of the boundary range, The release interval between batches and the number of sub-munitions per batch. For example, the calculations may be performed by the interceptor's controller 200 itself, in which case the interceptor may be equipped with a computer. In addition, the interceptor can also receive the ground radar or space reconnaissance satellite through its signal receiver 100, and the measurement result, that is, the detection of suspicious targets is completed by the ground radar or space reconnaissance satellite, and then the detection result can be sent to the interceptor. receiver 100. In addition, the controller of the interceptor can obtain the incoming target information through its detector and ground detection system at the same time, thereby further improving the detection accuracy and improving the interception efficiency.

In one embodiment, the release batches of the sub-munitions include a first batch, an intermediate batch and a final batch in sequence according to the release time, and the number of sub-munitions in the intermediate batch is larger than that of the first batch The number of sub-munitions delivered to the last batch and said final batch. For example, the intermediate batch includes multiple batches, and the number of sub-munitions put in each intermediate batch is greater than the number of sub-munitions put in the first batch and the final batch respectively. The embodiment of the present invention can achieve multi-level destruction of possible targets by releasing the sub-munitions in batches and adjusting the number of sub-munitions in each batch. In addition, by making the number of sub-munitions in the intermediate batches larger, the destruction efficiency can be improved. Probability of warheads (real warheads often fly hidden between fake warheads and decoys).

For example, in one embodiment, the release batches of the sub-munitions include multiple, and from the first batch to the last batch, the release interval of the sub-munitions first decreases and then increases, and the quantity of the ammunition to be released in each batch Increase first and then decrease. For example, when the enemy missile adopts various penetration measures, in order to avoid being detected by the detection device of the attacker, the true warhead tends to be hidden in the middle position. For example, the first drop of sub-munitions can be used to destroy penetration measures deployed in front of the real warhead (relative to the direction of movement of the incoming target), and later, in order to destroy the real target corresponding to the missile interception - the real warhead, the sub-munition's The amount can be greatly increased. The number of sub-munitions can be reduced due to the reduced probability of a true warhead being on the tail of a suspected target.

It should be noted that the attacking target referred to in the present invention may include real warheads (there may be one or more real warheads), fake warheads (eg, balloon camouflaged warheads), various baits or aluminum foils, etc.

Another aspect of the present invention provides a missile interception system. The interception system includes a detection module, a control module and a delivery module. The detection module is used to detect the flight trajectory and flight speed of the incoming missile. The control module is used to: calculate the preset launch time and preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interceptor carries sub-munitions; control the interceptor in the preset launching at the launch time, and flying along the preset flight trajectory, so as to enter the ammunition release area for the incoming missile at the first moment; and controlling the release module to release the incoming missile in the ammunition release area submunitions, so that the submunitions detonate in the interception area to destroy the incoming missile. The mid-section interception system of the ballistic missile of the present invention can destroy suspicious targets with a high probability by deploying the sub-munitions in the flight direction of the incoming target, thereby greatly reducing the precision requirements for the interceptor in impact interception.

In one embodiment, the detection module includes a radar. Radar is used to detect radar reflections of the incoming target in space. The control module is configured to calculate the boundary range of the interception area according to the radar reflection; and control the release module to release the sub-munitions according to the boundary range of the interception area, so that the dropped sub-munitions are in the same range as the interception area. Detonate at or before the bounding range of an intersection to destroy suspicious targets within said bounding range. The embodiment of the present invention detects the radar reflection of the incoming target by radar, and calculates the boundary range of the suspicious target according to the reflection, which can better determine the delivery timing and delivery method of the sub-munitions, thereby further improving the reliability of removing the threat target.

In one embodiment, the sub-munitions are equipped with delayed fuzes and/or trigger fuzes to detonate. On the one hand, the detonation time of the sub-munitions can be set in advance according to the position and speed of the bullets and the speed of the incoming target, so that the sub-munitions will be detonated when they move to the appropriate position relative to the suspicious target, so as to maximize the destruction. attack target. On the other hand, the sub-munitions can be configured to trigger detonating fuzes at the same time, so that a large number of munitions scattered in the air can be detonated when they come into contact with various suspicious targets, thereby improving the destruction effectiveness of suspicious targets. For example, when the trigger fuze is not triggered, the delay fuze can be detonated at a preset time (with the purpose of better destroying the incoming target), thereby avoiding the failure of the sub-munitions.

In this embodiment, preferably, each sub-munition ammunition is equipped with a delay fuze and a trigger fuze at the same time. For example, the delay fuze can be activated to detonate the sub-munitions only when the trigger fuze has not functioned for a certain period of time, thereby further improving the reliability of the destruction of suspected targets.

The ballistic missile mid-course interception method and system provided by the embodiments of the present invention can eliminate the threat of the payload carried by the ballistic missile in a large range by deploying a large number of sub-munitions on the flight trajectory of the incoming missile, thereby protecting the homeland security of the attacked country .

Yet another aspect of the present invention provides a memory. Wherein, the memory stores computer readable instructions. When the computer-readable instruction is invoked, the method for mid-course interception of a ballistic missile according to an embodiment of the present invention is performed.

Yet another aspect of the present invention provides a server. The server includes a memory and a processor, where the memory stores an executable program, and the controller is configured to invoke the executable program to execute the ballistic missile mid-course interception method of the embodiment of the present invention.

Those of ordinary skill in the art can realize that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Skilled artisans may implement the described functionality using different methods for each particular application, but such implementations should not be considered beyond the scope of the present invention.

Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working process of the above-described systems, devices and units may refer to the corresponding processes in the foregoing method embodiments, which will not be repeated here.

In the several embodiments provided in this application, it should be understood that the disclosed system, apparatus and method may be implemented in other manners. For example, the apparatus embodiments described above are only illustrative. For example, the division of the units is only a logical function division. In actual implementation, there may be other division methods. For example, multiple units or components may be combined or Can be integrated into another system, or some features can be ignored, or not implemented. On the other hand, the shown or discussed mutual coupling or direct coupling or communication connection may be through some interfaces, indirect coupling or communication connection of devices or units, and may be in electrical, mechanical or other forms.

The units described as separate components may or may not be physically separated, and components shown as units may or may not be physical units, that is, may be located in one place. Alternatively, it can be distributed over multiple network elements. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution in this embodiment.

In addition, each functional unit in each embodiment of the present invention may be integrated into one processing unit, or each unit may exist physically alone, or two or more units may be integrated into one unit.

The functions, if implemented in the form of software functional units and sold or used as stand-alone products, may be stored in a computer-readable memory. Based on this understanding, the technical solution of the present invention can be embodied in the form of a software product in essence, or the part that contributes to the prior art or the part of the technical solution. The computer software product is stored in a memory, including several The instructions are used to cause a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned memory includes: a U disk, a mobile hard disk, and a read-only memory (ROM, Read-Only Memory). Random access memory (RAM, Random, Access, Memory), magnetic disk or optical disk and other media that can store program check codes.

The above-described embodiments of the present invention can be combined with each other and have corresponding technical effects.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the scope of the present invention. within the scope of protection.

Claims (12)

1. a missile interception method, is characterized in that, comprises: S1 detects the flight trajectory and flight speed of the incoming missile; S2 calculates the preset launch time and preset flight trajectory of the interceptor according to the flight speed and the flight trajectory; wherein the interceptor carries sub-munitions; S3 makes the interceptor launch at the preset launch time, and fly along the preset flight trajectory, so as to enter the ammunition release area for the incoming missile at the first moment; S4, the interceptor drops sub-munitions on the incoming missile in the munition dropping area, so that the sub-munitions are detonated in the intercepting area to destroy the incoming missile; The flight trajectory and flight speed of the detection of incoming missiles include: detecting radar reflections of the incoming missile and its vicinity to calculate the boundary range of the interception area based on the radar reflections; The interceptor drops sub-munitions into the interception area in the munitions release area, so that the sub-munitions destroy the incoming missile in the interception area including: The interceptor drops submunitions in accordance with the shape and shape changes of the boundary range such that the dropped submunitions move toward the incoming missile in a first three-dimensional shape and intersect each other at least 50% of the boundary range After detonation. 2 . The missile interception method according to claim 1 , wherein the preset flight trajectory of the interceptor and the mid-course flight trajectory of the incoming missile at least partially overlap, and the interceptor is in the boundary range with the interceptor. 3 . A submunition is dropped prior to contact such that the submunition moves relative to the incoming missile along the coincident portion, and the submunition detonates upon at least partial intersection with the boundary range. 3 . The missile interception method according to claim 1 , wherein the first three-dimensional shape is an umbrella shape with an opening facing the incoming missile, a cone with a cone tip facing the incoming missile, and a diamond angle facing the incoming missile. 4 . At least one of the rhombus of the incoming missile and the cylindrical shape whose axis is in line with the direction of the flight trajectory of the incoming missile. 4 . The missile interception method according to claim 3 , wherein the size of the first three-dimensional shape in at least two spatial dimensions is larger than the boundary range. 5 . 5. The missile interception method according to claim 1, wherein, The interceptor enters within the boundary range at the second moment, and drops and detonates submunitions within the boundary range, thereby destroying the target within the boundary range. 6. The missile interception method according to any one of claims 1-5, characterized in that, The sub-munitions are detonated when the coincidence degree with the boundary range reaches a maximum, so as to destroy suspicious targets within the boundary range. 7. The missile interception method according to any one of claims 1 to 5, wherein the interceptor drops sub-munitions into the interception area in the ammunition dropping area, so that the sub-munitions are detonated in the interception area Before destroying incoming missiles include: Monitoring the movement speed and shape changes of the boundary range in space, and calculating the release timing, release interval, release batches, and sub-munitions in each batch according to the movement speed and shape changes quantity of medicine; The interceptor drops sub-munitions into the interception area in the munitions delivery area, so that the sub-munitions are detonated in the interception area to destroy the incoming missile including: The interceptor drops sub-munitions into the boundary range according to the release timing, the release interval, the release batch, and the number of sub-munitions dropped in each batch, so that the dropped sub-munitions meet the boundary range. detonated by time delay fuze and/or trigger fuze. 8. The missile interception method according to claim 7, characterized in that, before the interceptor drops sub-munitions, the method further comprises: calculating the relative velocity and relative position of the interceptor and the boundary range, and selecting sub-munitions accordingly The timing of drug delivery, and the selection of delivery batches, the delivery interval between batches, and the number of sub-munitions in each batch according to the shape and shape changes of the boundary range. 9 . The method for intercepting missiles according to claim 8 , wherein the drop batches of the sub-munitions include a first batch, an intermediate batch and a final batch in sequence according to the delivery time, and the intermediate batches are dropped. 10 . The quantity of the sub-munitions is greater than the delivery amount of the first batch and the final batch of sub-munitions. 10 . The missile interception method according to claim 9 , wherein the intermediate batch includes multiple batches, and the number of sub-munitions dropped in each intermediate batch is greater than that of the first batch and all the munitions. 11 . Describe the number of sub-munitions delivered separately in the final batch. 11 . The missile interception method according to claim 8 , wherein the delivery batches of the child and mother ammunition include multiple, and from the first batch to the last batch, the release interval of the child and mother ammunition first decreases and then increases. 12 . large, and the number of ammunition delivered in each batch first increases and then decreases. 12. A server, wherein the server comprises a memory and a processor, the memory storing an executable program, the processor for invoking the executable program to execute the missile according to any one of claims 1-11 intercept method.

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